Experimental Investigation Of Attenuation Of Strong Shock Waves In A Shock Tube With Hydrogen And Helium As Driver Gases

Author : Jim J. Jones
Publisher : Unknown
Page : 716 pages
File Size : 52,6 Mb
Release : 1957
Category : Helium
ISBN : STANFORD:36105024832425

Get Book

Experimental Investigation of Attenuation of Strong Shock Waves in a Shock Tube with Hydrogen and Helium as Driver Gases by Jim J. Jones Pdf

An experimental investigation has been made of the attenuation of strong shock waves in air in a shock tube. Time-history measurements were made of the static pressure at several stations in the wall of the tube. The internal diameter of the tube is 3.75 inches. shock-wave-velocity data were taken for a distance along the tube of about 120 feet.

Author : United States. National Advisory Committee for Aeronautics
Publisher : Unknown
Page : 902 pages
File Size : 47,5 Mb
Release : 1958
Category : Aeronautics
ISBN : RUTGERS:39030037544626

Get Book

Technical Note - National Advisory Committee for Aeronautics by United States. National Advisory Committee for Aeronautics Pdf

Author : Jack B. Esgar
Publisher : Unknown
Page : 732 pages
File Size : 42,7 Mb
Release : 1960
Category : Gas
ISBN : STANFORD:36105024742038

Get Book

Analytical Study of Soft Landings on Gas-filled Bags by Jack B. Esgar Pdf

Author : I. I. Glass,J. Gordon Hall
Publisher : Unknown
Page : 642 pages
File Size : 49,9 Mb
Release : 1959
Category : Aerodynamics, Supersonic
ISBN : UOM:39015104975050

Get Book

Handbook of Supersonic Aerodynamics by I. I. Glass,J. Gordon Hall Pdf

Author : Robert L. Trimpi,Nathaniel B. Cohen
Publisher : Unknown
Page : 66 pages
File Size : 55,7 Mb
Release : 1961
Category : Shock tubes
ISBN : UIUC:30112106632158

Get Book

A Nonlinear Theory for Predicting the Effects of Unsteady Laminar, Turbulent, Or Transitional Boundary Layers on the Attenuation of Shock Waves in a Shock Tube with Experimental Comparison by Robert L. Trimpi,Nathaniel B. Cohen Pdf

Summary: The linearized attenuation theory of NACA Technical Note 3375 is modified in the following manner: (a) an unsteady compressible local skin-friction coefficient is employed rather than the equivalent steady-flow incompressible coefficient; (b) a nonlinear approach is used to permit application of the theory to large attenuations; and (c) transition effects are considered. Curves are presented for predicting attenuation for shock pressure ratios up to 20 and a range of shock-tube Reynolds numbers. Comparison of theory and experimental data for shock-wave strengths between 1.5 and 10 over a wide range of Reynolds numbers shows good agreement with the nonlinear theory evaluated for a transition Reynolds number of 2.5 x 106.

Author : Johns Hopkins University. Applied Physics Laboratory, Silver Spring, Md
Publisher : Unknown
Page : 642 pages
File Size : 55,8 Mb
Release : 1950
Category : Aerodynamics, Supersonic
ISBN : UCAL:C3110461

Get Book

Handbook of Supersonic Aerodynamics by Johns Hopkins University. Applied Physics Laboratory, Silver Spring, Md Pdf

Author : United States. National Aeronautics and Space Administration
Publisher : Unknown
Page : 862 pages
File Size : 51,7 Mb
Release : 1960
Category : Aerodynamics
ISBN : UOM:39015039956795

Get Book

NASA Technical Report by United States. National Aeronautics and Space Administration Pdf

Author : Bernard E. Cunningham,Samuel Kraus
Publisher : Unknown
Page : 48 pages
File Size : 47,7 Mb
Release : 1962
Category : Aerodynamics
ISBN : UIUC:30112106873083

Get Book

A 1-foot Hypervelocity Shock Tunnel in which High-enthalpy, Real-gas Air Flows Can be Generated with Flow Times of about 180 Milliseconds by Bernard E. Cunningham,Samuel Kraus Pdf

Author : Anonim
Publisher : Unknown
Page : 722 pages
File Size : 41,8 Mb
Release : 1975
Category : Electronic
ISBN : MINN:31951000846554W

Get Book

NASA Technical Note by Anonim Pdf

Author : Aerospace Corporation
Publisher : Unknown
Page : 82 pages
File Size : 53,9 Mb
Release : 1963
Category : Boundary layer
ISBN : CORNELL:31924004403832

Get Book

Shock Tube Test Time Limitation Due to Turbulent Wall Boundary Layer by Aerospace Corporation Pdf

Shock tube test time limitation due to the premature arrival of the contact surface is analytically investigated for wholly turbulent wall boundary layers. The results are compared with those for wholly laminar wall boundary layers. Working curves are presented for more accurate estimates of test time in specific cases. (Author) -- NTRL website.

Author : Jim J. Jones
Publisher : Unknown
Page : 22 pages
File Size : 48,5 Mb
Release : 1959
Category : Aerodynamic heating
ISBN : UIUC:30112106741140

Get Book

Shock-tube Heat-transfer Measurements on Inner Surface of a Cylinder (simulating a Flat Plate) for Stagnation-temperature Range 4,100 ̊to 8,300 ̊R by Jim J. Jones Pdf

Author : F.R. Riddell
Publisher : Elsevier
Page : 768 pages
File Size : 52,9 Mb
Release : 2012-12-02
Category : Transportation
ISBN : 9780323142625

Get Book

Hypersonic Flow Research by F.R. Riddell Pdf

Progress in Astronautics and Rocketry, Volume 7: Hypersonic Flow Research compiles papers presented at a conference on hypersonics held at the Massachusetts Institute of Technology in August 1961. This book discusses the low Reynolds number effects, chemical kinetics effects, inviscid flow calculations, and experimental techniques relating to the problems in acquiring an understanding of hypersonic flow. The structure and composition of hypersonic wakes with attendant complex chemical kinetic effects is only briefly mentioned. This text consists of five parts. Parts A to C comprise of theoretical papers on the problems of calculating flow fields at hypersonic speeds. The experimental techniques that are of immediate practical interest in view of the difficulty of flight testing are discussed in Parts D and E. This publication is beneficial to engineers involved in advanced design problems.

Author : United States. National Advisory Committee for Aeronautics
Publisher : Unknown
Page : 716 pages
File Size : 47,8 Mb
Release : 1956
Category : Aeronautics
ISBN : OSU:32435062280276

Get Book

Research Abstracts and Reclassification Notice by United States. National Advisory Committee for Aeronautics Pdf

Author : Anonim
Publisher : Unknown
Page : 388 pages
File Size : 41,5 Mb
Release : 1957
Category : Aeronautics
ISBN : UVA:X004173287

Get Book

A Selected Listing of NASA Scientific and Technical Reports for ... by Anonim Pdf

Author : United States. National Advisory Committee for Aeronautics
Publisher : Unknown
Page : 388 pages
File Size : 42,5 Mb
Release : 1959
Category : Aeronautics
ISBN : UCBK:C029901327

Get Book

Index of NACA Technical Publications by United States. National Advisory Committee for Aeronautics Pdf